CN103991545B - A kind of taper rotary flapping wing thrust generating apparatus - Google Patents
A kind of taper rotary flapping wing thrust generating apparatus Download PDFInfo
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- CN103991545B CN103991545B CN201410234089.8A CN201410234089A CN103991545B CN 103991545 B CN103991545 B CN 103991545B CN 201410234089 A CN201410234089 A CN 201410234089A CN 103991545 B CN103991545 B CN 103991545B
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Abstract
A kind of taper rotary flapping wing thrust generating apparatus, belongs to vehicle technology field.It is made up of main shaft, pivoted arm, fin, wing axle, wing axis positioner, pilot bar and guides; Pivoted arm is vertical with main shaft to be connected, and wing axle acutangulates with pivoted arm and is connected, and wing axle is through wing axis positioner location, and wing axle is connected with fin, and the bearing pin of the open end that pilot bar is pitched by its U-shaped and fin are lived and connected, and the round bar of pilot bar is through guides.Under the driving of driving engine, fin is done taper and is rotated, and air of fluttering produces thrust, and efficiency is higher, and conveniently adjusts thrust direction, as the thruster of aircraft.
Description
Technical field
A kind of taper rotary flapping wing thrust generating apparatus, belongs to vehicle technology field, particularly relates to a kind of thruster for aircraft.
Background technology
Traditional flapping wing aircraft drives flapping wing by crankshaft-connecting rod mechanism, and flapping wing is fluttered up and down and produces thrust, and its efficiency is lower, is inconvenient to adjust thrust direction, and require higher to the strength at repeated alternation of flapping wing material.
Summary of the invention
The object of the invention is the above-mentioned defect overcoming traditional flapping wing aircraft thruster, invent a kind of taper rotary flapping wing thrust generating apparatus higher for the efficiency of aircraft.
A kind of taper rotary flapping wing thrust generating apparatus, is made up of main shaft, pivoted arm, fin, wing axle, wing axis positioner, pilot bar and guides.One end of main shaft is connected with aircraft fuselage by antifriction-bearing box, and one end of pivoted arm is vertical with the other end of main shaft to be connected, and the other end of pivoted arm and one end of wing axle are connected, and the angle of wing axle and pivoted arm is acute angle, and wing axle, pivoted arm and main shaft are in same plane; The other end of wing axle is connected in the leading edge place of fin by antifriction-bearing box and fin, wing axle is parallel with fin leading edge, and fin can around wing axle flexible rotating; The leading vertical of the end face of the close pivoted arm of fin and the root end face of fin and fin.Wing axis positioner is between fin and pivoted arm, and wing axle passes wing axis positioner and entangled by wing axis positioner, and wing axle around wing axis positioner center switch, but can not be able to move axially.Pilot bar is pitched by round bar, U-shaped and bearing pin forms, the closed end that one end of round bar and U-shaped are pitched is connected, round bar and U-shaped are pitched and are drawn a straight line, the bearing pin vertical with round bar that the open end that pilot bar is pitched by its U-shaped is installed and the fin root also close wing axle place being connected in fin alive, the plane of bearing pin vertically passing fin leading edge and trailing edge, the clearance of U-shaped fork thickness direction enough guarantees that the fin clipped can do the swing of fin in-plane neatly in U-shaped fork.Guides is fixedly bumped in oscillating bearing by linear bearing and forms; Guides is connected with the fuselage of aircraft by the shell of its oscillating bearing.The other end of round bar passes the linear bearing of guides, and round bar can do reciprocating linear motion neatly in linear bearing, and round bar can around the flexible switch in the center of guides.The U-shaped fork of composition pilot bar has enough length, to guarantee that the whole rotation process of fin can not be stuck; Round bar has enough length to guarantee that round bar does not deviate from guides in the whole rotation process of fin; Guides is installed near wing axis positioner as far as possible, but should guarantee that fin and U-shaped fork can not touch guides in the whole rotation process of fin; Main shaft and wing axis positioner are respectively in the both sides of pivoted arm plane of rotation, and wing axis positioner is on the extended line of main shaft, and guides and wing axis positioner are in the same side of pivoted arm plane of rotation; Guides is greater than the distance of wing axis positioner to pivoted arm plane of rotation to the distance of pivoted arm plane of rotation.
For reducing the resistance of air, improving 1ift-drag ratio, improving efficiency of fluttering, flat pattern or epirelief concave shape under the aerofoil profile employing epirelief of fin.
The principle of work of this kind of taper rotary flapping wing thrust generating apparatus is: the power of driving engine passes to main shaft after slowing down, main axis drives pivoted arm to rotate, pivoted arm drives wing axle to rotate, rotate at the traction lower panel of wing axle, due to the restriction of pilot bar and guides, in the plane that guides was in fin leading edge and trailing edge all the time or near, when fin rotates, its angle of attack revolves to turn around at a cycle of operations and interior regular change can occur, meet flapping wing, be conducive to producing thrust.Because guides is installed close to wing axis positioner, in one-period, the effect of flutterring generation under fin much larger than on flutter, the efficiency producing lift is higher.Change the size that rotating speed can change thrust, the direction of thrust is realized by the relative height of change guides and main shaft.Because the angle of wing axle and pivoted arm is acute angle, and be subject to the restriction of wing axis positioner, in the left and right sides of wing axis positioner, the rotational trajectory of wing axle is taper, only needs shorter pivoted arm, and the scope of fluttering of fin is larger, efficiency is high, and this is simple and compact for structure, lightweight construction; Make tapered circumference due to fin to rotate, rotating speed is higher, can produce larger thrust, and less demanding to the strength at repeated alternation of material.
Accompanying drawing explanation
Fig. 1 is the schematic diagram of a kind of taper rotary flapping wing of the present invention thrust generating apparatus.
In figure, 1-main shaft, 2-pivoted arm, 3-wing axis positioner, 4-wing axle, 5-fin, 6-pilot bar, 61-round bar, 62-U shape is pitched, 63-bearing pin, 7-guides, 71-linear bearing, 72-oscillating bearing; The hand of rotation of the arc representation main shaft 1 of main shaft 1 place band arrow.
Detailed description of the invention
Now 1 citing is illustrated the present invention by reference to the accompanying drawings: a kind of taper rotary flapping wing thrust generating apparatus, is made up of main shaft 1, pivoted arm 2, fin 5, wing axle 4, wing axis positioner 3, pilot bar 6 and guides 7.One end of main shaft 1 is connected with flapping wing aircraft fuselage by antifriction-bearing box, one end of pivoted arm 2 is vertical with the other end of main shaft 1 to be connected, the other end of pivoted arm 2 and one end of wing axle 4 are connected, the angle α of wing axle 4 and pivoted arm 2 is between 30 ° ~ 60 °, and wing axle 4, pivoted arm 2 and main shaft 1 are in same plane; The other end of wing axle 4 is connected in the leading edge place of fin 5 by antifriction-bearing box and fin 5, wing axle 4 is parallel with fin 5 leading edge, and fin 5 can around wing axle 4 flexible rotating; The leading vertical of the end face of the close pivoted arm 2 of fin 5 and the root end face of fin 5 and fin 5.Wing axis positioner 3 is swivel bearings (swivelbearing), wing axis positioner 3 is between fin 5 and pivoted arm 2, wing axle 4 passes wing axis positioner 3 and is entangled by wing axis positioner 3, wing axle 4 can around wing axis positioner 3 center switch, the maximum taper of switch is greater than 120 °, but can not move axially.Pilot bar 6 is made up of round bar 61, U-shaped fork 62 and bearing pin 63; The closed end that one end of round bar 61 and U-shaped pitch 62 is connected, round bar 61 and U-shaped are pitched 62 and are drawn a straight line, the bearing pin 63 vertical with round bar 61 root also close wing axle 4 place that be connected in fin 5 alive with fin 5 that the open end that pilot bar 6 pitches 62 by its U-shaped is installed, the plane of bearing pin 63 vertically passing fin 5 leading edge and trailing edge, the clearance that U-shaped pitches 62 thickness directions enough guarantees that the fin 5 clipped can pitch at U-shaped the swing making fin 5 in-plane in 62 neatly.Guides 7 is fixedly bumped in oscillating bearing 72 by linear bearing 71 and forms; Guides 7 is connected with the fuselage of flapping wing aircraft by the shell of its oscillating bearing 72.The other end of round bar 61 passes the linear bearing 71 of guides 7, and round bar 61 can do reciprocating linear motion neatly in linear bearing 71, and round bar 61 can around the flexible switch in the center of guides 7.The U-shaped fork 62 of composition pilot bar 6 has enough length, to guarantee that the whole rotation process of fin 5 can not be stuck; Round bar 61 has enough length to guarantee that round bar 61 does not deviate from guides 7 in the whole rotation process of fin 5; Guides 7 is installed near wing axis positioner 3 as far as possible, but should guarantee that fin 5 and U-shaped fork 62 can not touch guides 7 in the whole rotation process of fin 5; Main shaft 1 and wing axis positioner 3 are respectively in the both sides of pivoted arm 2 plane of rotation, and wing axis positioner 3 is on the extended line of main shaft 1, and guides 7 and wing axis positioner 3 are in the same side of pivoted arm 2 plane of rotation; Guides 7 to the distance of pivoted arm 2 plane of rotation between wing axis positioner 3 1.3 times ~ 2.5 times of distance to pivoted arm 2 plane of rotation.
For reducing the resistance of air, improving 1ift-drag ratio, improving efficiency of fluttering, flat pattern or epirelief concave shape under the aerofoil profile employing epirelief of fin 5.
The principle of work of this kind of taper rotary flapping wing thrust generating apparatus is: the power of driving engine passes to main shaft 1 after slowing down, main shaft 1 rotates and drives pivoted arm 2 to rotate, pivoted arm 2 drives wing axle 4 to rotate, rotate at the traction lower panel 5 of wing axle 4, due to the restriction of pilot bar 6 and guides 7, in the plane that guides 7 was in fin 5 leading edge and trailing edge all the time or near, when fin 5 rotates, its angle of attack revolves to turn around at a cycle of operations and interior regular change can occur, meet flapping wing, be conducive to producing thrust.When fin 5 rotates a circle, the concrete change procedure of its angle of attack is: suppose that guides 7 and main shaft 1 are in same level, now guides 7 is zero with the relative height of main shaft 1, suppose that the reference position that fin 5 rotates is the position of fin 5 near guides 7, now the angle of attack of fin 5 is negative 90 °, along with the rotation of wing axle 4 is drawn, fin 5 upward movement, the absolute value of the angle of attack is reduced to rapidly 0 °, now pilot bar 6 is tangent with the rotating cone of wing axle 4 above the horizontal surface crossing main shaft 1, and rear wing axle 4 continues to rotate, the angle of attack of fin 5 more slowly becomes 90 ° from 0 °, now pilot bar 6 level, fin 5 is away from guides 7, along with the continuation of wing axle 4 is drawn, fin 5 moves downward, the angle of attack more slowly becomes 0 ° from 90 °, now pilot bar 6 is tangent at the rotating cone of the below of horizontal surface and wing axle 4 of crossing main shaft 1, along with the continuation of wing axle 4 rotates, the angle of attack of fin 5 becomes rapidly negative 90 ° by 0 °, now get back to reference position, complete a swing circle.Because guides 7 is installed close to wing axis positioner 3, in one-period, the fin effect of flutterring generation for 5 times much larger than on flutter, the efficiency producing lift is higher.Change the size that rotating speed can change thrust, the direction of thrust realizes with the relative height of main shaft 1 by changing guides 7.Because wing axle 4 and the angle of pivoted arm 2 are acute angle, and be subject to the restriction of wing axis positioner 3, in the left and right sides of wing axis positioner 3, the rotational trajectory of wing axle 4 is taper, only needs shorter pivoted arm 2, and the scope of fluttering of fin 5 is larger, efficiency is high, and this is simple and compact for structure, lightweight construction; Make tapered circumference due to fin 5 to rotate, rotating speed is higher, can produce larger thrust, and less demanding to the strength at repeated alternation of material.
Use this contrive equipment can produce larger thrust on board the aircraft in couples.
Claims (5)
1. a taper rotary flapping wing thrust generating apparatus, is characterized in that: be made up of main shaft (1), pivoted arm (2), wing axis positioner (3), wing axle (4), fin (5), pilot bar (6) and guides (7); One end of pivoted arm (2) is vertical with main shaft (1) to be connected, and the other end and the wing axle (4) of pivoted arm (2) are connected, and wing axle (4) is acute angle with the angle of pivoted arm (2), and wing axle (4), pivoted arm (2) and main shaft (1) are in same plane; Wing axle (4) is connected in fin (5) leading edge place by antifriction-bearing box and fin (5), and wing axle (4) is parallel with fin (5) leading edge; Wing axis positioner (3) is between fin (5) and pivoted arm (2), and wing axle (4) is through wing axis positioner (3) and entangled by wing axis positioner (3); Pilot bar (6) pitches (62) by round bar (61), U-shaped and bearing pin (63) forms, the closed end that one end of round bar (61) and U-shaped pitch (62) is connected, the bearing pin (63) vertical with round bar (61) root also close wing axle (4) place that be connected in fin (5) alive with fin (5) that the open end that pilot bar (6) pitches (62) by its U-shaped is installed, the plane of bearing pin (63) vertically passing fin (5) leading edge and trailing edge; Guides (7) is fixedly bumped in oscillating bearing (72) by linear bearing (71) and forms; The other end of round bar (61) passes the linear bearing (71) of guides (7); Main shaft (1) and wing axis positioner (3) are respectively in the both sides of pivoted arm (2) plane of rotation, and guides (7) and wing axis positioner (3) are in the same side of pivoted arm (2) plane of rotation; Guides (7) is greater than the distance of wing axis positioner (3) to pivoted arm (2) plane of rotation to the distance of pivoted arm (2) plane of rotation.
2. a kind of taper rotary flapping wing thrust generating apparatus according to claim 1, is characterized in that: the angle (α) of wing axle (4) and pivoted arm (2) is between 30 ° ~ 60 °.
3. a kind of taper rotary flapping wing thrust generating apparatus according to claim 1, is characterized in that: flat pattern or epirelief concave shape under the aerofoil profile employing epirelief of fin (5).
4. a kind of taper rotary flapping wing thrust generating apparatus according to claim 1, is characterized in that: wing axis positioner (3) is a swivel bearing.
5. a kind of taper rotary flapping wing thrust generating apparatus according to claim 1, is characterized in that: guides (7) to the distance of pivoted arm (2) plane of rotation between wing axis positioner (3) 1.3 times ~ 2.5 times of distance to pivoted arm (2) plane of rotation.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410234089.8A CN103991545B (en) | 2014-05-30 | 2014-05-30 | A kind of taper rotary flapping wing thrust generating apparatus |
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| CN201410234089.8A CN103991545B (en) | 2014-05-30 | 2014-05-30 | A kind of taper rotary flapping wing thrust generating apparatus |
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| Publication Number | Publication Date |
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| CN103991545A CN103991545A (en) | 2014-08-20 |
| CN103991545B true CN103991545B (en) | 2016-01-06 |
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| CN104843186B (en) * | 2015-05-14 | 2017-03-01 | 许允夫 | A kind of drive mechanism of the wing of flapping-wing aircraft |
Citations (6)
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|---|---|---|---|---|
| CN102180262A (en) * | 2011-03-24 | 2011-09-14 | 王志成 | Telescopic flapping wing lifting force generation device |
| CN102180263A (en) * | 2011-04-02 | 2011-09-14 | 王志成 | External gear engaged flapping wing raising force generation device |
| CN102862678A (en) * | 2012-09-02 | 2013-01-09 | 王志成 | Moving guide frame type reciprocating airfoil lift force generating device |
| CN102862679A (en) * | 2012-09-02 | 2013-01-09 | 王志成 | Movable guide rod type reciprocating wing lifting force generation device |
| CN102887225A (en) * | 2012-10-11 | 2013-01-23 | 王志成 | Flapping wing lift force generator with wing frames unidirectionally rotating |
| CN203864999U (en) * | 2014-05-30 | 2014-10-08 | 佛山市神风航空科技有限公司 | Tapered rotating flapping wing thrust generating device |
-
2014
- 2014-05-30 CN CN201410234089.8A patent/CN103991545B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102180262A (en) * | 2011-03-24 | 2011-09-14 | 王志成 | Telescopic flapping wing lifting force generation device |
| CN102180263A (en) * | 2011-04-02 | 2011-09-14 | 王志成 | External gear engaged flapping wing raising force generation device |
| CN102862678A (en) * | 2012-09-02 | 2013-01-09 | 王志成 | Moving guide frame type reciprocating airfoil lift force generating device |
| CN102862679A (en) * | 2012-09-02 | 2013-01-09 | 王志成 | Movable guide rod type reciprocating wing lifting force generation device |
| CN102887225A (en) * | 2012-10-11 | 2013-01-23 | 王志成 | Flapping wing lift force generator with wing frames unidirectionally rotating |
| CN203864999U (en) * | 2014-05-30 | 2014-10-08 | 佛山市神风航空科技有限公司 | Tapered rotating flapping wing thrust generating device |
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| CN103991545A (en) | 2014-08-20 |
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Inventor after: Li Li Inventor before: Wang Zhicheng |
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Effective date of registration: 20170908 Address after: 301, room 5, unit 14, Yingbin District, Funing Town, Funing County, Qinhuangdao, Hebei 066000, China Patentee after: Li Li Address before: Foshan City, Guangdong province 528500 city streets Gaoming District No. 78 Jiangwan Road, room 402 Fu Wan Patentee before: FOSHAN SHENFENG AVIATION TECHNOLOGY Co.,Ltd. |
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Effective date of registration: 20180627 Address after: 226561 twenty-two groups of Lake Liu village, Rugao Town, Nantong City, Jiangsu Province Patentee after: NANTONG JUXING CASTING AND FORGING Co.,Ltd. Address before: 066000 301 unit, 5 unit 301, Yingbin District, Funing Town, Funing, Qinhuangdao, Hebei, China Patentee before: Li Li |
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Denomination of invention: Thrust generating device for conical rotary flapping wing Effective date of registration: 20210927 Granted publication date: 20160106 Pledgee: Bank of China Limited Rugao Branch Pledgor: NANTONG JUXING CASTING AND FORGING Co.,Ltd. Registration number: Y2021980009954 |
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Date of cancellation: 20221031 Granted publication date: 20160106 Pledgee: Bank of China Limited Rugao Branch Pledgor: NANTONG JUXING CASTING AND FORGING Co.,Ltd. Registration number: Y2021980009954 |
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| PC01 | Cancellation of the registration of the contract for pledge of patent right |